Wing rock is a rolling motion characterized by self-excited oscillations which appears at high angles of attack in aircraft with highly-swept wings. In this paper an analyti- cal model describing this phenomenon is presented for simple wing and wing-fuselage layouts. The parameters of the model were derived through numerical tting of ex- perimental data. For both cases an L1 adaptive controller is applied to suppress the wing rock motion for dierent angles of attack and initial conditions. Adaptation ca- pability is assessed testing the controller action on a model subjected to parametric disturbances. The controller can suppress the motion with satisfactory performance for both congurations, even when disturbed.